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Airfoil Structure Shim

Inactive Publication Date: 2009-08-27
SIEMENS ENERGY INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Such a shim is disadvantageous because it is susceptible to loosing its spring force, allowing relative motion of a corresponding blade or vain resulting in wear.

Method used

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  • Airfoil Structure Shim
  • Airfoil Structure Shim
  • Airfoil Structure Shim

Examples

Experimental program
Comparison scheme
Effect test

first embodiment

[0024]In FIG. 1, an airfoil structure / shim / retention member combination 10 constructed in accordance with the present invention is illustrated. The airfoil structure / shim / retention member combination 10 is adapted to be used in a gas turbine (not shown) of a gas turbine engine (not shown). The gas turbine engine may include a compressor (not shown), a combustor (not shown), and a turbine (not shown). The compressor compresses ambient air. The combustor combines the compressed air with a fuel and ignites the mixture creating combustion products defining a working gas. The working gases travel to the turbine. Within the compressor are a series of rows of stationary vanes and rotating blades. Each pair of rows of vanes and blades is called a stage. For each row of blades, a separate rotor disc is provided. The rotor discs form part of a shaft and rotor disc assembly. One or more of the rotor discs is provided with a dovetail slot extending 360 degrees about the disc so as to receive do...

second embodiment

[0031]In FIG. 2, an airfoil structure / shim / retention member combination 100 constructed in accordance with the present invention is illustrated. The airfoil structure / shim / retention member combination 100 comprises an airfoil structure 120, a shim 130 and a retention member 140. The retention member 140 comprises a retention casing 150 fixedly coupled to a housing H of the gas turbine engine. The retention casing 150 is provided with a dovetail slot 152 extending 360 degrees about the retention casing 150. At a base of the dovetail slot 152, a recess 154 is provided.

[0032]The airfoil structure 120 comprises a vane 122 having a dovetail root or base 124, a platform 126 and an exposed blade portion 128. The dovetail base 124 is provided with a recess 127. As noted above, the retention casing 150 is provided with a dovetail slot 152. The retention casing dovetail slot 152 is adapted to receive a dovetail base 124 of a vane 122. The vane dovetail base 124 functions to couple the vane 12...

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PUM

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Abstract

An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity.

Description

FIELD OF THE INVENTION[0001]The present invention is directed to a shim to be received in a cavity defined by a first recess in an airfoil structure and a second recess in a retention member and, further, is directed to an airfoil structure, shim and retention member combination.BACKGROUND OF THE INVENTION[0002]A conventional combustible gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses ambient air. The combustor combines the compressed air with a fuel and ignites the mixture creating combustion products defining a working gas. The working gases travel to the turbine. Within the compressor are a series of rows of stationary vanes and rotating blades. Each pair of rows of vanes and blades is called a stage. The rotating blades are coupled to a shaft and rotor disc assembly.[0003]For each row of blades, a separate rotor disc is provided. The rotor discs form part of the shaft and rotor disc assembly. One or more of the rotor discs is provi...

Claims

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Application Information

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IPC IPC(8): F01D5/32
CPCF05D2260/30F01D5/3038
Inventor WIEBE, DAVID J.FINNERAN, JOHN W.SAMUELSON, JEFFERY W.CHARRON, RICHARD C.
Owner SIEMENS ENERGY INC